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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 100,000
Max Cl/Cd: 64.58 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe456-il-100000-n5.txt
Download as CSV file: xf-goe456-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3090   0.11325   0.10865  -0.0381   1.0000   0.0321
  -8.500  -0.3138   0.11153   0.10701  -0.0372   1.0000   0.0322
  -8.250  -0.3204   0.11003   0.10560  -0.0359   1.0000   0.0322
  -7.750  -0.3182   0.10287   0.09856  -0.0314   1.0000   0.0332
  -7.500  -0.3209   0.10061   0.09636  -0.0289   1.0000   0.0339
  -7.250  -0.3237   0.09859   0.09439  -0.0276   0.9991   0.0346
  -7.000  -0.3073   0.09487   0.09067  -0.0317   0.9931   0.0358
  -6.750  -0.2906   0.09109   0.08689  -0.0366   0.9863   0.0370
  -6.500  -0.2693   0.08690   0.08270  -0.0432   0.9789   0.0389
  -6.250  -0.2354   0.08281   0.07858  -0.0592   0.9683   0.0418
  -6.000  -0.2082   0.07842   0.07413  -0.0678   0.9597   0.0421
  -5.750  -0.2033   0.07400   0.06975  -0.0624   0.9570   0.0451
  -5.500  -0.1824   0.07042   0.06613  -0.0662   0.9495   0.0478
  -5.250  -0.1262   0.06436   0.05986  -0.0863   0.9423   0.0551
  -4.750  -0.0842   0.05398   0.04936  -0.0894   0.9303   0.0285
  -4.250  -0.0025   0.04037   0.03514  -0.1051   0.9182   0.0212
  -4.000   0.0386   0.03473   0.02905  -0.1112   0.9148   0.0205
  -3.750   0.0681   0.03051   0.02427  -0.1135   0.9067   0.0202
  -3.500   0.1060   0.02665   0.01967  -0.1164   0.9026   0.0202
  -3.250   0.1375   0.02431   0.01667  -0.1171   0.8962   0.0212
  -3.000   0.1700   0.02205   0.01390  -0.1182   0.8906   0.0235
  -2.750   0.2060   0.02027   0.01177  -0.1196   0.8869   0.0252
  -2.500   0.2324   0.01916   0.01043  -0.1190   0.8783   0.0276
  -2.250   0.2670   0.01807   0.00911  -0.1200   0.8738   0.0346
  -2.000   0.2941   0.01732   0.00814  -0.1196   0.8652   0.0423
  -1.750   0.3280   0.01612   0.00729  -0.1207   0.8602   0.1381
  -1.500   0.3547   0.01614   0.00736  -0.1205   0.8510   0.2234
  -1.250   0.3861   0.01591   0.00699  -0.1211   0.8448   0.2502
  -1.000   0.4134   0.01570   0.00667  -0.1208   0.8360   0.2643
  -0.750   0.4429   0.01549   0.00637  -0.1209   0.8282   0.2840
  -0.500   0.4731   0.01525   0.00608  -0.1213   0.8205   0.3107
  -0.250   0.5006   0.01503   0.00590  -0.1212   0.8115   0.3525
   0.000   0.5303   0.01438   0.00571  -0.1215   0.8048   0.5031
   0.500   0.5933   0.01358   0.00543  -0.1225   0.7875   1.0000
   0.750   0.6208   0.01366   0.00537  -0.1223   0.7785   1.0000
   1.000   0.6473   0.01378   0.00539  -0.1220   0.7691   1.0000
   1.250   0.6766   0.01383   0.00533  -0.1221   0.7617   1.0000
   1.500   0.7019   0.01400   0.00544  -0.1216   0.7517   1.0000
   1.750   0.7288   0.01412   0.00551  -0.1214   0.7432   1.0000
   2.000   0.7563   0.01424   0.00560  -0.1212   0.7350   1.0000
   2.250   0.7819   0.01439   0.00575  -0.1208   0.7248   1.0000
   2.500   0.8083   0.01450   0.00583  -0.1203   0.7140   1.0000
   2.750   0.8345   0.01458   0.00588  -0.1198   0.7015   1.0000
   3.000   0.8602   0.01466   0.00600  -0.1191   0.6876   1.0000
   3.250   0.8854   0.01477   0.00610  -0.1183   0.6725   1.0000
   3.500   0.9103   0.01490   0.00625  -0.1175   0.6572   1.0000
   3.750   0.9355   0.01506   0.00649  -0.1168   0.6432   1.0000
   4.000   0.9611   0.01526   0.00677  -0.1163   0.6319   1.0000
   4.250   0.9864   0.01548   0.00710  -0.1157   0.6205   1.0000
   4.500   1.0098   0.01570   0.00742  -0.1146   0.6024   1.0000
   4.750   1.0269   0.01590   0.00754  -0.1120   0.5547   1.0000
   5.000   1.0397   0.01633   0.00768  -0.1087   0.4771   1.0000
   5.250   1.0414   0.01783   0.00815  -0.1040   0.3100   1.0000
   5.500   1.0422   0.02009   0.00943  -0.1001   0.1751   1.0000
   5.750   1.0406   0.02267   0.01105  -0.0959   0.0302   1.0000
   6.000   1.0558   0.02375   0.01227  -0.0937   0.0232   1.0000
   6.250   1.0697   0.02498   0.01372  -0.0913   0.0206   1.0000
   6.500   1.0840   0.02615   0.01519  -0.0890   0.0194   1.0000
   6.750   1.0972   0.02734   0.01660  -0.0867   0.0177   1.0000
   7.000   1.1071   0.02860   0.01806  -0.0840   0.0160   1.0000
   7.250   1.1135   0.03006   0.01970  -0.0808   0.0153   1.0000
   7.500   1.1188   0.03163   0.02141  -0.0776   0.0149   1.0000
   7.750   1.1240   0.03338   0.02327  -0.0746   0.0145   1.0000
   8.000   1.1329   0.03524   0.02520  -0.0721   0.0143   1.0000
   8.250   1.1505   0.03730   0.02728  -0.0706   0.0140   1.0000
   8.750   1.2240   0.04420   0.03438  -0.0730   0.0118   1.0000
   9.000   1.2495   0.04728   0.03783  -0.0726   0.0118   1.0000
   9.250   1.2699   0.05092   0.04179  -0.0717   0.0119   1.0000
   9.500   1.2891   0.05582   0.04699  -0.0710   0.0122   1.0000
  10.250   1.3004   0.06184   0.05402  -0.0619   0.0133   1.0000
  10.500   1.2889   0.06383   0.05644  -0.0573   0.0139   1.0000
  10.750   1.2761   0.06664   0.05965  -0.0535   0.0145   1.0000
  11.000   1.2639   0.07000   0.06336  -0.0507   0.0151   1.0000
  11.250   1.2503   0.07382   0.06749  -0.0487   0.0156   1.0000
  11.500   1.2357   0.07786   0.07180  -0.0473   0.0161   1.0000
  11.750   1.2197   0.08227   0.07645  -0.0467   0.0164   1.0000
  12.000   1.2027   0.08699   0.08140  -0.0468   0.0167   1.0000
  12.250   1.1848   0.09215   0.08678  -0.0478   0.0169   1.0000
  12.500   1.1667   0.09768   0.09251  -0.0495   0.0170   1.0000
  12.750   1.1484   0.10370   0.09872  -0.0521   0.0171   1.0000
  13.000   1.1300   0.11024   0.10542  -0.0556   0.0171   1.0000
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